WIND TUNNEL INVESTIGATION TO DETERMINE AERODYNAMIC CHARACTERISTICS OF A 0.03-SCALE MODEL OF THE TITAN III/MOL LAUNCH CONFIGURATION DURING THE ABORT SEQUENCE AT MACH NUMBERS FROM 0.60 TO 3.00

Abstract

A 0.03-scale model of the Titan III/Manned Orbiting Laboratory (MOL) launch vehicle was tested in Tunnels 16T and 16S of the Propulsion Wind Tunnel Facility at Mach numbers from 0.6 to 3.0 to obtain aerodynamic force and moment data on the airborne vehicle during the abort sequence. Test results show that there was a reduction in magnitude of the pitching-moment and normal-force coefficients at all angles of attack as jet pressure ratio was increased. Thrust termination (jet off to jet on) resulted in an increase in the magnitude of both the yawing-moment and side-force coefficients at all angles of attack.

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Document Details

Document Type
Technical Report
Publication Date
Aug 01, 1967
Accession Number
AD0818288

Entities

People

  • D. A. Maclanahan Jr.
  • M. L. Homan

Organizations

  • Arnold Engineering Development Complex

Tags

Communities of Interest

  • Space
  • Weapons Technologies

DTIC Thesaurus Topics

  • Aerodynamic Characteristics
  • Aerodynamic Forces
  • Air Force
  • Coefficients
  • Data Reduction
  • Flow
  • Government Procurement
  • Governments
  • Launch Vehicles
  • Mach Number
  • Measurement
  • Rocket Engines
  • Scale Models
  • Solid Propellants
  • Test Facilities
  • Vehicles
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Aerodynamics/Aeronautics.
  • Aerospace Test and Evaluation

Technology Areas

  • Space
  • Space - Hall-Effect Thruster
  • Space - Spacecraft Maneuvers